Multirotor Flight Control for Rotary-Wing Fault Detection
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Solution Overview
Problem
Multirotor helicopters used in industrial applications face challenges in maintaining operation when faults occur in their driving systems, such as motor failures, due to severe use environments like high winds, which can lead to accidents if not managed effectively.
Innovation Solution
A control device for unmanned aircraft that includes a rotary-wing control signal generation circuit, a measuring device, and a fault detection circuit to detect and respond to faults by adjusting control signals and distribution of control amounts among the rotor wings, allowing the aircraft to continue operation even if a fault occurs.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If fault detection and control adjustment mechanisms are added to handle rotor failures, then the reliability and ability to continue operation is improved, but the device complexity increases
Solution Approach 1:
The patent implements preliminary action by pre-configuring the control system with fault detection capabilities and pre-programmed control amount distribution strategies. The control device includes a fault detection unit that continuously monitors rotor status and a control amount distribution unit that automatically adjusts control signals based on detected faults, eliminating the need for complex real-time decision-making during emergencies.
Solution Approach 2:
The control system performs self-service by automatically detecting faults and adjusting control amounts without external intervention. The control amount distribution unit uses feedback from the fault detection unit to autonomously recalculate and redistribute control signals among remaining healthy rotors, enabling the aircraft to self-correct and continue operation.
2Reliability
If control amounts are dynamically redistributed among rotor wings when faults occur, then the ability to maintain flight is improved, but the control system complexity increases
Solution Approach 1:
The patent applies dynamics by implementing a dynamic control amount distribution mechanism that automatically adapts to changing system conditions. When a rotor fault is detected, the control amount distribution unit dynamically recalculates the optimal control signal distribution among remaining healthy rotors based on current flight parameters and fault characteristics, allowing the system to flexibly respond to various failure modes.
Solution Approach 2:
The control system implements feedback by continuously monitoring rotor performance through the fault detection unit and using this information to adjust control amount distribution. The control amount distribution unit receives feedback signals about rotor status and flight conditions, then modifies control signals accordingly to maintain stable flight despite rotor failures.
Data Source
AI summary
[Problem to be Solved]The object is to provide a device, a method and the like which, when a fault occurs, particularly when a fault occurs in an operation of some of rotary wings, can control a flight depending on the fault, or which can be at least used for control when a fault occurs, or which can detect the fault.[Solution]A control device for unmanned aircraft comprising: a rotary-wing control signal generation circuit for generating a rotary wing control signal for causing a driving device to drive a plurality of rotary wings for flying the unmanned aircraft; a measuring device for measuring a physical amount relating to an operation of at least one of the plurality of rotary wings; and a fault detection circuit for detecting a fault in the operation of at least one of the plurality of rotary wings by using the physical amount measured by the measuring device, wherein the rotary-wing control signal generation circuit is configured to generate a rotary wing control signal depending on the fault detected by the fault detection circuit in the operation of at least one of the plurality of rotary wings, is provided.